Method for defending an aircraft against a frontal attack

ABSTRACT

A method for defending an aircraft against a frontal attack by an interceptor comprising, launching a rocket in the direction of travel of said aircraft, said rocket containing in a collapsed condition a collapsible reflector having three orthogonal surfaces of wire mesh, then ejecting said reflector from said rocket whereupon said reflector is expanded, and then towing said reflector whereby said reflector serves as a target for attracting said interceptor.

United States Patent 2,763,002 9/1956 Fitzgerald eta].

[72] Inventors James C. Hiester 343/188 Baltimore, Md.; 2,957,41710/1960 Musgrave 343/18X Harry L. Van Trees, Jr., Watertown, Mass.FOREIGN PATENTS 3; 9Y $7321 1960 746,300 3/1956 Great Britain... 343/1sclag} f 21971 834,596 5/1960 Great Britain 343/18B 9 [73] Assignee theUnited States of America as represented OTHER REFERENCES by theSecretary ofthe Navy Aviation Week; Nov. 18, 1957; pages 50, 51, 53, 57and 59; Nov. 25, 1957; pages 105 and 106; Copy in Scientific Library343-18 Primary Examiner-Rodney D. Bennett, Jr. AssistantExaminer-Malcolm F. Hubler [54] METHOD FOR DEFENDING AN AIRCRAFTAttorneys-W. O. Quesenberry, N. H. Losche and P. S.

AGAINST A FRONTAL ATTACK Collignon 1 Claim, 2 Drawing Figs.

U.S. A method for defending an aircraft against a frontal l51 l Cl Hmq15/20 attack by an interceptor comprising, launching a rocket in theFleld of Search direction of travel of aircraft aid rocket containing ina 35/25 (cursory); 343/18 13 (C), 13 coilapsed condition a collapsiblereflector having three orthogonal surfaces of wire mesh, then ejectingsaid reflector [56] References Clted from said rocket whereupon saidreflector is expanded, and UNITED STATES PATENTS then towing saidreflector whereby said reflector serves as a 2,490,793 12/1949 Fleming343/1813 target for attracting said interceptor.

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METHUD FDR DEFENDENG AN AIRCRAFT AGAHNST A FRONTAL ATTAQK The presentinvention relates to a device for providing forward hemisphere defensefor military aircraft against enemy interceptors that might be equippedwith either guns, rockets, or air-to-air missiles. The device will alsoprovide protection for an aircraft against surface to air missiles.

Various methods have been employed in the past to guard a militaryaircraft, such as a bomber, against enemy attack from the front ororward hemisphere. One method consists of the use of electroniccountermeasure equipment to jam or deceive the guidance or locatingequipment of the enemy interceptor. However, it is highly probable thatmany enemy interceptor-s are being equipped with antijam equipment, andelectronic countermeasure devices cannot be relied upon to give completeprotection.

Another method of defending a military aircraft against a frontal attackhas been by the use of forward firing turrets. However, forward firingturrets cannot be readily located in present day high speed aircraft sothat the turret will have access to the interceptor.

The present invention provides a novel method of protecting a militaryaircraft from a frontal attack by providing another target to attractthe interceptor. A rocket is launched from the military aircraft to beprotected, and upon launching, a corner reflector is ejected from therocket and towed behind the rocket. 'lhe rocket accelerates atapproximately 100 feet per second until the rocket is approximately 1000feet in front of the military aircraft and then the rocket maintains avelocity of about .1000 feet per second until its fuel is ex hausted.The towed target consists of three orthogonal surfaces of wire mesh thatprovides a reflecting surface that will attract the interceptor.

It is therefore a general object of the present invention to provide animproved method and apparatus for defending a military aircraft againsta frontal attack.

Another object of the present invention is to provide an im provedtarget for attracting an interceptor away from a military aircraft.

Other objects and advantages of the present invention will be readilyappreciated as the same becomes better understood by reference to thefollowing detailed description when considered in connection with theaccompanying drawing in which:

FIG. 1 is a side view, partially in section, showing a tow-target foldedwithin a rocket; and

FIG. 2 is a perspective view showing a target being towed behind arocket.

Referring now to the drawing, a rocket 11, which is pro vided with asuitable engine 9 having a plurality of ports 10, is mounted to anaircraft in a manner such that it will be launched ahead of theaircraft. A tow-target l2 is provided which will fold up and be carriedwithin the rocket ll during transport by the military aircraft.

Tow-target 12 is comprised of three orthogonal surfaces which arebordered by tubular rings 13,14, and 115. Each of rings l3, l4, and 15are suitably hinged so that they can be folded to a relatively smallsize in order to fit within rocket ll, as shown in FIG ll of thedrawing. Wire mesh 16 is attached to each of rings l3 l4, and i5 toprovide a reflecting surface. By making the reflective area equal to orslightly greater than that of the parent aircraft, the probability ofpreventing a hit of the parent aircraft is relatively high.

in operation, one or more of the rockets with tow-targets therein, aremounted to the aircraft by a conventional pod or launching rack. Thetime of launching the rocket will depend upon the type of missionemployed by an enemy. if the primary threat is a surface-to-air missile,the optimum time for launching will be during tracking by an enemy radarin order to cause the attacking system to lock onto the rocket.

When the attack is from an air-to-air missile ll! the forwardhemisphere, the rocket can be launched during any phase of the attack inorder to cause the enemy missile to break lock on the parent aircraftand. track the rocket. For a direct nose-on, air-to-air missile attack,the rocket will cause the fuse in the missile to detonate prematurely.

As soon as the rocket is launched, the corner reflector is ejected andopened to provide a radar target. The corner reflector might be ejectedby any well-known means such as by springs or by compressed air. Therocket is accelerated until it is approximately 1000 feet in front ofthe parent aircraft, and then the rocket maintains a constant velocityof approximately lOOO feet per second until burn-out. The acceleratingforce may be provided by a solid or liquid propellant motor which iswell-known to those skilled in the missile launching art. By way ofexample, a single engine may be provided which will provide anaccelerating force for a given period of time, and then provide asustaining force for an additional period of time. As the departure fromthe parent aircraft is not radical, the rocket an target areparticularly effective, as velocity discriminating radars do not detectthe change and it is highly probably that the towed target will betracked instead of the parent aircraft.

It can thus be seen that the present invention provides a novel methodof preventing the destruction of an aircraft that is being attacked froma forward hemisphere. Obviously many modifications and variations of thepresent invention are possible in the light of the above teachings. Itis therefore to be understood, that within the scope of the'appendedclaims, the invention may be practiced otherwise than as specificallydescribed.

We claim:

1. A method for defending an aircraft against a frontal attack by aninterceptor comprising, launching a rocket in the direction of travel ofsaid aircraft, said rocket containing in a collapsed condition acollapsible reflector having three orthogonal surfaces of wire mesh,then ejecting said reflector from said rocket whereupon said reflectoris expanded, and then towing said reflector whereby said reflectorserves as a target for attracting said interceptor.

1. A method for defending an aircraft against a frontal attack by aninterceptor comprising, launching a rocket in the direction of travel ofsaid aircraft, said rocket containing in a collapsed condition acollapsible reflector having three orthogonal surfaces of wire mesh,then ejecting said reflector from said rocket whereupon said reflectoris expanded, and then towing said reflector whereby said reflectorserves as a target for attracting said interceptor.